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    A GAS TURBINE ENGINE CONTROL SYSTEM AND METHOD FOR LIMITING TURBINE OVERSPEED IN CASE OF A SHAFT FAILURE
    2.
    发明公开
    A GAS TURBINE ENGINE CONTROL SYSTEM AND METHOD FOR LIMITING TURBINE OVERSPEED IN CASE OF A SHAFT FAILURE 审中-公开

    公开(公告)号：EP4390064A1

    公开(公告)日：2024-06-26

    申请号：EP22216427.9

    申请日：2022-12-23

    申请人： Rolls-Royce Deutschland Ltd & Co KG

    发明人： CALDERON, Jorge

    IPC分类号： F01D21/04 ,  F01D17/16 ,  F02C9/52 ,  F02C9/54

    CPC分类号： F01D21/045 ,  F02C9/52 ,  F02C9/54 ,  F01D17/162 ,  F05D2270/02120130101 ,  F05D2270/0920130101

    摘要： The invention regards a gas turbine engine control system and a method for limiting turbine overspeed in case of a shaft failure. The control system comprises an overspeed protection system (4) which is able to detect a shaft failure, a variable stator vane mechanism (6), wherein the variable stator vane mechanism (6) is configured to adjust variable stator vanes (66) of a compressor in their rotational position, wherein the variable stator vane mechanism (6) is activated to move at least one row of the variable stator vanes (66) into a closed position which blocks air flow through the compressor in case a shaft failure is detected, and bleed valves (121) in the compressor having a closed position and an opened position, wherein the bleed valves (121) are configured to divert in the opened position airflow through the compressor to a bypass channel of the gas turbine engine. It is further provided a detection system (67) detecting directly or indirectly the position of at least one row of the variable stator vanes (66), wherein the control system is configured to set the bleed valves (121) to the opened position when the detection system (67) detects that the at least one row of variable stator vanes (66) has moved into the closed position.

    Power plant start-up method
    3.
    发明公开
    Power plant start-up method 审中-公开
    电厂启动方法

    公开(公告)号：EP2562395A3

    公开(公告)日：2018-02-28

    申请号：EP12180612.9

    申请日：2012-08-16

    申请人： General Electric Company

    发明人： Ouellet, Noemie Dion ,  Snook, Daniel David ,  Wichmann, Lisa Anne ,  Draper, Samuel David ,  Rittenhouse, Scott Allen

    IPC分类号： F02C7/277 ,  F01D13/02 ,  F01D15/10 ,  F01D19/00 ,  F02C3/36 ,  F02C6/06 ,  F02C7/18 ,  F02C9/52

    CPC分类号： F02C7/277 ,  F01D13/02 ,  F01D19/00 ,  F02C3/36 ,  F02C7/18 ,  F02C9/52 ,  F05D2220/76 ,  F05D2260/85 ,  F05D2270/061 ,  F05D2270/082 ,  Y02T50/675 ,  Y02T50/677

    摘要： Ambient air is compressed into a compressed ambient gas flow (26) and delivered to a turbine combustor (32). An exhaust port is opened. A turbine shaft (22) is rotated at an ignition speed and a fuel stream (28) is delivered to the turbine combustor (32) for mixing with the compressed ambient gas flow (26) to form a combustible mixture. The combustible mixture is burned and forms a recirculated gas flow (50) that drives the turbine (34). The recirculated gas flow (50) is recirculated using a recirculation loop (52). The turbine (34) is operated at a target speed and then reaches substantially stoichiometric combustion. At least a portion of the recirculated gas flow (50) is extracted using an extraction conduit (48) that is fluidly connected to the turbine compressor (30).

    摘要翻译： 环境空气被压缩成压缩的环境气流（26）并被输送到涡轮燃烧器（32）。 排气口打开。 涡轮轴（22）以点火速度旋转并且燃料流（28）被输送到涡轮燃烧器（32）以与压缩的环境气流（26）混合以形成可燃混合物。 可燃混合物被燃烧并形成驱动涡轮机（34）的再循环气流（50）。 再循环气流（50）使用再循环回路（52）再循环。 涡轮机（34）以目标速度运行并且然后基本上达到化学计量燃烧。 使用流体连接到涡轮压缩机（30）的抽取导管（48）抽取再循环气流（50）的至少一部分。

    GAS TURBINE CONTROL METHOD AND DEVICE
    5.
    发明公开
    GAS TURBINE CONTROL METHOD AND DEVICE 审中-公开

    公开(公告)号：EP2184467A4

    公开(公告)日：2017-12-13

    申请号：EP09714483

    申请日：2009-02-23

    申请人： MITSUBISHI HITACHI POWER SYS

    发明人： NOMURA MASUMI ,  MIYAUCHI KOTARO

    IPC分类号： F02C9/00 ,  F02C9/52 ,  F02C9/54

    CPC分类号： F02C9/52 ,  F02C9/28 ,  F02C9/54 ,  F05D2270/114 ,  F05D2270/14 ,  F05D2270/301 ,  F05D2270/3061 ,  F05D2270/332 ,  F05D2270/334

    摘要： A gas turbine control method for preventing then operation from deviating from the operating state at the ideal fuel and air flow-rates expected when the gas turbine is designed and maintaining an efficient operating state. A gas turbine control device comprises a frequency analyzing means for analyzing the frequencies inside the combustor of a gas turbine, a state grasping means for grasping the combustion state in the gas turbine on the basis of a state signal representing the result of the analysis by frequency band, the amount of operation process including a ratio between the air flow rate and pilot fuel in the gas turbine, the atmosphere state, and the load amount, a combustion characteristic grasping means for grasping the characteristic of the combustion vibration, and a control section for calculating a correction value of at least either the air flow rate supplied to the combustor or the pilot ratio from the grasped combustion vibration characteristic and the grasped combustion state each time the degree of the combustion vibration exceeds a predetermined control value, correcting the initial design values of the air flow rate and the pilot ratio predetermined correspondingly to the amount of operation process and the state signal, and thereby driving the gas turbine. The control section resets the correction of the initial design values when the degree of combustion vibration of the gas turbine is below the predetermined control value for a given period of time and operates the gas turbine using the initial design values.

    AUXILIARY POWER UNIT ASSEMBLY AND A METHOD OF USING THE SAME
    7.
    发明公开
    AUXILIARY POWER UNIT ASSEMBLY AND A METHOD OF USING THE SAME 审中-公开
    VILFAHREN ZUR VERWENDUNG DAVON HILFSTRIEBWERKANORDNUNG

    公开(公告)号：EP3127816A1

    公开(公告)日：2017-02-08

    申请号：EP16178301.4

    申请日：2016-07-07

    申请人： Rolls-Royce plc

    发明人： Stieger, Rory ,  Razak, Ahmad

    IPC分类号： B64D41/00 ,  F02C7/32

    CPC分类号： B64D13/04 ,  B64D13/06 ,  B64D41/00 ,  B64D2013/0611 ,  B64D2013/0644 ,  B64D2013/0688 ,  B64D2041/002 ,  F02C7/042 ,  F02C9/26 ,  F02C9/28 ,  F02C9/52 ,  F02C9/54 ,  F05D2220/32 ,  F05D2220/50 ,  F05D2270/06 ,  F05D2270/335

    摘要： A gas turbine auxiliary power unit system (100:200:300:400:500) for an aircraft comprises an aircraft cabin (110) provided with a pressurised air supply (116), a gas turbine engine (120:220:320:420:520) comprising a compressor assembly (122:222:322:422:522), and a controller (130:230:330:430:530).
    The pressurised air supply (116) is provided to the aircraft cabin (110) through an aircraft cabin air inlet (112), and exhausted from the aircraft cabin (110) through an aircraft cabin air exhaust (114), while the gas turbine engine (120:220:320:420:520) is provided with an inlet air flow (124) from the aircraft cabin air exhaust (114).
    The controller (130:230:330:430:530) is operable to control a flow rate of a fuel supplied to the gas turbine engine (120:220:320:420:520) responsive to a power demand on the auxiliary power unit (100:200:300:400:500), and also to restrict an inlet air flow into the gas turbine engine (120:220:320:420:520), so as to maintain an air pressure inside the aircraft cabin (110) within a pre-determined range.

    摘要翻译： 用于飞行器的燃气轮机辅助动力单元系统（100：200：300：400：500）包括设置有加压空气供应装置（116）的飞机机舱（110），燃气涡轮发动机（120：220：320：420 ：520），包括压缩机组件（122：222：322：422：522）和控制器（130：230：330：430：530）。 加压空气供应装置（116）通过飞机机舱空气入口（112）提供给飞机机舱（110），并通过飞行器机舱排气（114）从飞机机舱（110）排出，而燃气涡轮发动机 （120：220：320：420：520）设置有来自飞机机舱排气口（114）的入口空气流（124）。 控制器（130：230：330：430：530）可操作以响应于对辅助动力单元的电力需求来控制供应到燃气涡轮发动机（120：220：320：420：520）的燃料的流量 （100：200：300：400：500），并且还限制进入燃气涡轮发动机（120：220：320：420：520）的入口空气流，以保持飞机机舱 ）在预定范围内。